Application of Sampled-Data Control Techniques in the Design of an Aircraft Flutter Mode Controller.

摘要

The problem of designing a sampled-data flutter mode controller using optimal control techniques is investigated. The plant being controlled is the Control Configured Vehicle NB-52. The continuous equations of motion about the longitudinal aircraft axis are discretized by the state transition method. Using the discrete equations of motion the discrete linear regulator problem is solved. An acceptable set of quadratic weightings is developed for the full-state feedback problem. Full-state feedback is not physically realizable so it is necessary to solve the suboptimal problem. The infinite time discrete linear stochastic regulator problem is developed and solved. The radient derived in this development is used in a performance minimization by conjugate gradients algorithm to derive the best suboptimal feedback gains. A digital simulation is performed that demonstrates a successful design. (Author)